JP2001514994A - Preloaded bearing assembly for mounting and retaining aircraft propeller blades. - Google Patents

Abstract

SUMMARY A propeller blade mounting and retaining assembly (10) of the present invention having a hub portion (12) rotating about a propeller axis is disclosed. The assembly includes a blade receiver (14) for attaching the blade to the hub, and an inner surface (24) of a hub arm (22) for interacting the receiver with the hub. The receiver (14) is located within the hub arm (22), but is not integral with the vane and the inner surface of the hub arm. A mounting and retaining mechanism (18) is used to retain the blade receiver (14) to the hub arm (22), which are mutually rotatable. Prior to the centrifugal load in the operation of the propeller blades, a preloading device (16) for applying a preload to the holding mechanism (18) is provided. The blade is separable from the blade receiver (14) without impairing the operability of the holding mechanism (18).

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001] Technical Field The present invention generally intended to relate to aircraft propeller blades of variable pitch, mounting retaining assembly obtained by adding a preload for the propeller blade and more particularly (preloaded
retention assembly).

[0002] In the design of aircraft propeller blades BACKGROUND Modern invention uses a composite material to produce a lightweight blades capable of supporting the operation load. These operating loads include a centrifugal force component acting in a direction parallel to the axis of the propeller blade. Historically, no preload has been added (non-
The operation of the preloaded propeller blade retention system depends on the load capacity, especially the centrifugal load created by the weight of the blade structure to enhance the retention of the blade against steady and periodic bending loads. . As propeller blades have become lighter through the use of composite materials, non-preloaded propeller blade retention systems have been modified to apply the load required to enhance blade retention. This modification eventually resulted in large, heavy parts.

[0003] Modern propeller blade retention systems can address size issues and result in weight savings. Many of these systems use a bearing assembly for mounting and retaining propeller blades inside the hub assembly. For example, U.S. Patent No.
No. 4,921,403 includes a bearing configuration using roller bearings. Such a bearing configuration retains the propeller blades from inside the hub and also reduces vibration. However, this design does not provide the means to apply the preload required in a holding system including modern composite blades. There is prior art that addresses the need to add preload. U.S. Patent No.
No. 4,850,801 discloses a bearing arrangement with means for applying a preload. However, in such a configuration, the blades are directly connected (interf
It is not easy to replace and maintain parts because they are aced). Replacing the blade requires removal of the bearing components, which further complicates maintenance. In addition, the cost and complexity of the tools required to perform routine maintenance increases. The connection of the propeller blades to the holding components not only requires a more complex design of the blade roots, but also limits the types of blades that can be used in the system.

[0004] To address the need for flexibility in the connection of multiple propeller blades, some modern applications use receiving means. In such an application, the vane interacts only with the receiver. The receiver also interacts with the holding system. Therefore, simplification can be achieved because the blade part is not designed to interact with the holding system. An example using a receiving means is disclosed in U.S. Pat.
No. 2 discloses it. This patent differs from this design in that it uses roller bearings to hold and rotate the propeller blades. Also, unlike the present invention, the patent uses an annular fastener threaded to the hub to achieve system preload. While this type of retention mechanism addresses the size and weight issues of the retention mechanism, an inherent limit that causes stress concentrations to occur in the threads of the hub.
ation), which can be operated at periodic high fatigue loads, resulting in hub failure. Similarly, the aforementioned U.S. Pat. No. 4,850,801 uses a threaded fastener that interacts with the threaded portion of the hub, thus providing a similar high stress on the hub. The present invention does not include a threaded portion on any of the three main parts of the propeller assembly, namely, the hub, the receiver, or the propeller blades.

[0005] Accordingly, there is a need for a propeller blade holding system that co-exists a functionally separable blade and holding device, preloads the holding mechanism, resulting in reduced cost and parts, and further reduces maintenance complexity. It is.

[0006] The first An object of the present invention is to retain the attachment holding portion of the propeller blades to provide a device for adding a preload, assembly can be completely functionally separate from the propeller blades Yes, reducing component complexity, assembly complexity, and maintenance complexity and cost.

Another object of the present invention is to provide a propeller blade preload and receiver including a receiver that can connect a mounting and retaining mechanism assembly and a preload system to a plurality of blade types without having to complicate the blade root design. It is to provide a mounting and holding system.

It is another object of the present invention to provide a system for retaining and applying preload to a propeller blade, the system comprising an individual receiving portion and an angular contact ball between the receiving portion and the propeller hub. The use of a bearing allows the use of a one-piece spherical groove and does not include a thread in the receiver, hub or vane of the propeller device.

It is yet another object of the present invention to provide a system for mounting and retaining a blade to apply a preload, the system adapted to receive a hydraulic actuator adapted to provide a portion of the preload. A smaller and easier to use tool is available for tightening the preload nut with respect to the preload of the receiving part using the preload.

The foregoing four objects and advantages are achieved by the propeller blade mounting and retaining assembly of the present invention for use with a propeller having a hub that rotates about a propeller axis.
The assembly includes a blade receiver for attaching the blade to the hub, and an inner surface of the hub arm for interacting the receiver with the hub. The receiver is located within the hub arm and is not integral with the vane and the inner surface of the hub arm. An attachment and holding mechanism is used to attach and hold the blade receiving portion to the hub arm portion and to be rotatable between them. A preload device is provided to apply a preload to the mounting and holding mechanism prior to applying a centrifugal load in the operation of the propeller blades. The blades are separable from the blade receiver without compromising the operability of the mounting and retaining mechanism.

Further, the four objects and advantages set forth above are achieved by another embodiment of a propeller blade mounting and holding assembly according to the present invention for use with a propeller having a hub rotatable about a propeller axis. The assembly has a blade receiver for attaching the blade portion to the hub, and an inner surface of the hub arm portion for interacting the receiving portion with the hub portion. The receiving portion is located within the hub arm portion, is integral with the blade portion, and is not integral with the inner surface of the hub arm. The mounting and holding mechanism is used to mount and hold the blade receiver to the inner surface of the hub arm and to be rotatable relative to each other. A preload device is provided for applying a preload to the mounting and holding mechanism prior to applying a centrifugal load in propeller blade operation. The mounting and retaining mechanism includes an angular contact ball bearing assembly to facilitate relative rotational movement between the receiver and the inner surface of the hub arm. The angular contact ball bearing assembly has an integral, non-divided groove.

[0012] showing the attaching and holding assembly of the propeller blades of the present invention described in Embodiment Figure 1 and reference numeral 10 in FIG. 2 embodiment of the invention. Normally, the propeller blade holding assembly 10 includes four divided parts, a hub part 12, a receiving part 14, a preloading means 16, and a mounting holding means 18. The receiving section 14 is located inside the hub arm section 22. The receiving part 14 and the hub arm part 22 interact with the preload means 16 and the mounting holding means 18. The holding means 18 is arranged between the receiving section 14 and the hub arm section 22.

In general, the hub arm 22 has a cylindrical shape defined by an inner surface 24 and an outer surface 23 that extend radially about the axis of rotation of the vane and receiver.
As shown in FIG. 2, the hub arm 22 is usually cylindrical and has a hub barrel.
) 34. 2, the inner surface 24 of the hub arm 22 is
It includes a hub arm shelf 30, a first groove 32 outside the inboard, which is a unitary, non-segmented structure and a ball groove relief area near the torso. ) 33, all of which extend circumferentially on the inner surface 24. A torso ball groove relief area 33 near the lower portion of the first groove 32 is circumferentially rounded or chamfered around the hub 12 to facilitate mounting of the torso ball bearing assembly 39. Used for A hub arm shelf including a first side surface 35 substantially perpendicular to the second cylindrical side surface 31 and adjacent to the first groove 32 near the body-side end 61 on the inner surface 24 of the hub arm portion 22. The part 30 is formed. The hub arm shelf 30 extends circumferentially around the inner surface 24 of the hub arm portion 22 and is utilized to bottom the mounting and retaining assembly elements 36 to assist in preloading during assembly. used.

As shown in FIGS. 1 and 1A and 2, the mounting and retaining assembly element 36 is generally cylindrical in shape and has functionally shaped inner and outer surfaces, and as described below, Threads 37 on the surface and a second bearing groove 38 outside the blade outboard, a stepped surface 41 for engaging the seal, and a rounded surface 43 Include the top and bottom inner surfaces, respectively. As shown in FIGS. 1 and 1A, the upper end of element 36 is defined by a plurality of extensions 85 described below.

As shown in FIG. 2, the receiver 14 has an integral mounting joint 40 formed at the top end 42 of the receiver 14 for interacting with the propeller blades 44, thereby providing air The foil blade 44 can be removed from the propeller of the aircraft without affecting the preload of the blade mounting and retaining means 18. The mounting joint 40 includes a fastener opening 45 for engaging a fastener (not shown) for securing the propeller blades 44. A bulkhead 46 for supporting and strengthening the second joint 40 to which the propeller blades 44 are attached is provided on the bottom side 4 of the second attachment joint 40.
At 8 it is formed as an integral structure. A third groove 50 on the outer side, near the blade, is radially rounded or chamfered toward the blade-side end 53 of the receiving portion 14. The third groove 50 faces the second bearing groove 38 of the mounting and retaining assembly element 36 to form a ball groove 58 near the blade. The fourth groove 60 on the inner side near the body is provided with the receiving portion 14 near the end 61 on the body side.
At a slight distance above, the fourth groove 60 is rounded or chamfered circumferentially around the outer side surface 52 of the receiving portion 14, where the fourth groove 60 is inverted with respect to the first groove of the hub arm portion 22. The ball groove 59 is formed and installed on the side, and is located near the body. In order to provide clearance for mounting and holding the receiving portion 14 inside the hub arm portion 22, a ball groove portion 59 near the body and a ball groove portion 58 near the blade are formed in the relief region 33.
, An angular contact ball bearing assembly 39 near the fuselage, which is easier to install, and a ball groove 58 formed on the outside 52 of the receiving portion 14.
Each is used to secure an angular contact ball bearing assembly 64 near the blade which is easier to install due to the adjacent relief area 63. The receiver 14 is preferably designed to accommodate the use of a hydraulic or mechanical actuator (not shown) used to change the pitch of the propeller blades 44 at the base.

Each of the body-side ball bearing assembly 39 and the blade-side ball bearing assembly 64, together with each of the body-side ball groove 59 and the blade-side ball groove 58, form an angular contact ball bearing device, and have a line of force. The angular positioning indicated by C _F allows the use of a single, undivided spherical groove. This precludes the use of a split support ball groove in the prior art of US Pat. No. 5,415,527. Ball bearing assembly 39 near the fuselage and ball bearing assembly 6 near the blade
Each of the 4 allows rotation of the blade portion inside the hub arm portion 22. For a particular aircraft load, a rotating element and a ball groove shape are formed.
The angle of the line of intersection of these lines of force indicated by the bearing ball grooves 58, 59 and the line C _F, unlike many prior art bearings does not form an angle (non-angularly oriented bearings), assignee A wider "wheelbase" or "cone of contact" similar to that disclosed in U.S. Pat. No. 5,118,256 assigned to U.S. Pat. Centrifugal loads, preloads, and bending loads, as well as thrust loads and torque loads, act according to conical contacts that provide a more stable blade mounting and retaining mechanism. Each of the ball bearing assemblies 39, 64, along with a hydraulic actuator (not shown), allows the pitch angle to be varied.

As shown in FIG. 2, the preload means 16 includes a ring-shaped preload nut 70 and a thread portion 7.
1 that engage and mate with the threads 37 of the mounting and retaining assembly element 36. The preload is achieved by pressing against the top surface 54 of the hub arm 22 and tightening the preload nut 70, thereby creating a load parallel to the axis of rotation of the propeller blades 44. Limiting the inward movement by loading the ball bearing assembly 64 outwardly through the element 36 against the bodyward ball bearing assembly 39;
Generates a force that applies a preload. The circumferential fixed seal 72 is attached to the hub arm 2.
2 between the top surface 54 and the load nut 70 to prevent leakage of lubricating oil contained in the hub arm for components of the propeller blade retaining mechanism and the blade pitch changing actuator. The maximum possible exposure of the lubricant on all interacting surfaces of the components of the mounting retainer enables the components of the propeller blade mounting retainer assembly 10 to maintain normal operation. It is.
A second circumferential stationary seal 74 supported and secured in place by a preload locking ring 76 is disposed between the preload nut 70 and the mounting and retaining assembly element 36.

The retaining ring portion 76 not only prevents the preload nut portion 70 from backing off the thread portion 37 of the mounting and retaining assembly element 36, but also provides a dynamic seal.
al) Supports 78, thereby preventing loss of preload of mounting and retaining means 18. As shown in FIGS. 1 and 2, the retaining ring 76 having its legs 77 extending between the preload nut 70 and the element 36 has a T-shaped cross-section and a circumferential Extending in the direction. Preferably, the retaining ring is split to facilitate mounting after the preload nut is in place. In the preferred embodiment, FIG.
As shown, ring 76 includes inner legs 79 defined by a plurality of fingers 81 separated by slots 83. The slot between the fingers 81 engages the extension 85 of FIG. 1A extending from the element 36. Bolts 86 are tightened through the top side 88 of the retaining ring 76 to secure the retaining ring 76 in place with respect to the preload nut 70. The engagement of the slot 83 with the extension 85 locks the retaining ring 76 in place with respect to the element 36. Thus, the dual locking configuration of the locking ring 76 (i.e., the engagement of the bolt 86 with the preload nut 70 and the engagement of the slot 83 with the extension 85) is defined by the position of the preload nut relative to the thread 37. At such a required preload position, a fixed position between the preload nut 70 and the element 36 is obtained. The splittable nature and the multiple element / preload nut engagement positions of the retaining ring 76 allow for mounting at any relative position between the nut 70 and the element 36. As shown in FIG. 1, a spring-loaded dynamic seal 78 is disposed between the outer surface 87 of the receiving portion 14 and the stepped surface 41 of the mounting and retaining assembly element 36 to maintain the sealing contact pressure. A backup ring 82 made of a durable material, and the surface thereof is disposed between the fixed seal 74 and the preload nut 70, and functions as a support of the seal near the body. A second backup ring 84 is disposed between the kinetic seal 78 and the retaining ring 76 to reduce friction and prevent the kinetic seal 78 from being dragged on the retaining ring 76.

In the assembly shown, a dynamic seal 78 and a backup ring 84 are mounted toward the blade-side end 53 of the outer side 87 of the receiver 14. The mounting and retaining element 36 with the preload nut 70, the stationary seals 72, 74 and the backup ring 82 provide a groove 60 near the fuselage and a groove near the blade so that the ball bearing assembly 64 near the blade can be pressed into the bearing groove 38. It slides on the receiving part 14 in the middle of the groove 50. The ball bearing assembly 64 close to the blade is inserted into a predetermined position using the relief area 63. Blade receiver 14 and bearing assembly 64 slide into hub arm 22 adjacent inner surface 24. Element 36
Bottom is on the side surface 35 of the shelf 30. A torso bearing assembly 39 is mounted from inside the hub utilizing the relief area 33. As described above, the assembly is pushed outward against the hub arm 22. The preload nut 70 is manually tightened at the threaded portion 37 of the element 36 to secure the component in place until the next application of preload and to tighten the component against the surface 24 of the hub arm 22. . The preload can be performed using only the preload nut 70 or, alternatively, incorporating a thickened septum 46 in the receiving portion design to reduce the hydraulic actuator application to the surface 48 of the septum 46 or the receiving portion 14. It is adapted as an assembly tool that opposes the base 90 and provides some significant retention preload. This option allows the preload nut 70 to be tightened to the hub arm 22 using a smaller tool. Thus, the required preload is provided by a hydraulic actuator, if desired, and by a preload tool (not shown) using the septum 46 or the base 90 of the receiver 14. The preload nut 70 is tightened as necessary, and the application of the preload is completed. If using a hydraulic actuator (not shown), remove it. Depending on the deflection of the hub, it may be necessary to apply a preload in stages. Then, not only the motion seal 78 and the fixed seals 72 and 74, and the fixed ring 76 and the bolt 86 but also the respective backup rings 84 and 82 are attached to complete the assembly.

In operation, each of the inner and outer ball bearing assemblies 39, 64 allows the blades to rotate within the hub arm 22, and controls the pitch and the number of revolutions per minute of the propeller. When the pitch is changed by a hydraulic actuator (not shown) different from the actuator for applying the preload, the ball bearing assembly 39,
64 is rotatable in the circumferential direction around the hub arm 22.

In another embodiment 110 according to the present invention shown in FIG. 3, the receiving portion 114 is formed as a unitary structure as the root 191 of the propeller blade 144, and is not described again here, but is similar in the drawing. They include all other features according to the invention described above. Additional features shown in FIGS. 1 and 2 but not shown in FIG. 3 are also part of embodiment 110, but are not described here. As is known in the art,
During the blade formation process, the blade is formed as an integral structure with the receiver 114. As described above, the integral non-divided groove 13 differs from the prior art.
The use of 2, 138, 150 and 160 prevents deterioration of the groove. Also,
An angular contact ball bearing assembly is used.

A first advantage of the present invention is that parts of the assembly are fully functionally separable from the propeller blades, reducing the complexity of parts and tools. Reducing complexity results in lower costs. Another advantage of the present invention is that the propeller blade preload and mounting and retaining system allows the mounting and retaining mechanism assembly and preload system to be adapted to multiple blade types without the need to complicate blade root design. It is to include. A further advantage of the present invention is the use of angled and contacting ball bearings and individual receivers between the mounting and retaining assembly and the preload system and propeller hub, thereby allowing the use of integral grooves and split grooves. Avoids the potential problems associated with the joints, which include threads on the hub, blades, or the receiver of the propeller assembly. A further advantage of the present invention is to use a receiver with a hydraulic actuator adapted to provide a portion of the preload so that a smaller, more manageable tool can be used to tighten the preload nut with respect to the receiver preload. It was done.

While the present invention has been described with respect to particular embodiments thereof, those skilled in the art will recognize that this embodiment may be modified and modified in various ways without departing from the scope and spirit of the invention. Let's do it.

[Brief description of the drawings]

FIG. 1 shows a hub arm portion, a receiving portion, a mounting and holding mechanism, and a preload applying mechanism (preload mechanis).
FIG. 4 is a three-dimensional cutaway view of the propeller blade mounting and holding assembly including m).

FIG. 1A is an enlarged perspective view of an element indicated by an arrow 1A in FIG. 1;

2 is a cross-sectional view of the propeller blade retaining assembly of FIG. 1;

FIG. 3 is a cross-sectional view of a propeller blade retaining assembly in another embodiment.

[Procedural Amendment] Submission of translation of Article 34 Amendment of the Patent Cooperation Treaty

[Submission date] February 7, 2000 (2000.2.7)

[Procedure amendment 1]

[Document name to be amended] Statement

[Correction target item name] Full text

[Correction method] Change

[Correction contents]

Patent application title: Preloaded bearing assembly for mounting and retaining propeller blades for aircraft

[Claims]

DETAILED DESCRIPTION OF THE INVENTION

[0001] Technical Field The present invention generally intended to relate to aircraft propeller blades of variable pitch, mounting retaining assembly obtained by adding a preload for the propeller blade and more particularly (preloaded
retention assembly).

[0002] In the design of aircraft propeller blades BACKGROUND Modern invention uses a composite material to produce a lightweight blades capable of supporting the operation load. These operating loads include a centrifugal force component acting in a direction parallel to the axis of the propeller blade. Historically, no preload has been added (non-
The operation of the preloaded propeller blade retention system depends on the load capacity, especially the centrifugal load created by the weight of the blade structure to enhance the retention of the blade against steady and periodic bending loads. . As propeller blades have become lighter through the use of composite materials, non-preloaded propeller blade retention systems have been modified to apply the load required to enhance blade retention. This modification eventually resulted in large, heavy parts.

[0003] Modern propeller blade retention systems can address size issues and result in weight savings. Many of these systems use a bearing assembly for mounting and retaining propeller blades inside the hub assembly. For example, U.S. Pat. No. 4,921,403 includes a bearing configuration using roller bearings. Such a bearing configuration holds the propeller blades from inside the hub and also reduces vibration. However, this design does not provide the means to apply the preload required in a holding system including modern composite blades. There is prior art that addresses the need to add preload. U.S. Pat. No. 4,850,801 (based on the two-part form of independent claim 1) discloses a bearing arrangement with means for applying a preload. A threaded fastener interfaces with the threaded portion of the hub, thus creating high stress on the hub. The fastener section includes a relief area for the introduction of the ball of the ball bearing on the outboard, which includes a moving seal and associated seals for interacting with the ball and the fixing means of the bearing. Parts are placed.

[0004] To address the need for flexibility in the connection of multiple propeller blades, some modern applications use receiving means. In such an application, the vane interacts only with the receiver. The receiver also interacts with the holding system. Therefore, simplification can be achieved because the blade part is not designed to interact with the holding system. An example using a receiving means is described in U.S. Pat.
No. 3,352. This patent uses roller bearings to hold and rotate the propeller blades. The patent also uses a ring-shaped fastener that is threaded to the hub to achieve system preload. While this type of retention mechanism addresses the size and weight issues of the retention mechanism, it also has inherent limitations that cause stress concentrations to occur in the threads of the hub, which can lead to high periodicity. Operated under fatigue loading, which can result in hub failure.

In the invention of US Pat. No. 5,015,150 referred to herein, a tension nut engages a thread on a hub for retaining an outer ring of a double row tapered roller bearing.
ning nut). The inner bearing element threaded with the blade part holds the split inner ring of the bearing, and in GB-A-2 244 525, the hub part engages with a preload element for a bearing with split grooves. And German Patent Application No. 43 15 080 use a bearing having a split inner groove and a split preload nut.

[0006]Summary of the Invention  Propeller with hub rotating about propeller shaft and propeller according to the invention
A blade retainer is provided that attaches the blade to the hub.
Means for interfacing the receiving means with the hub portion, the receiving means being located within the interacting means, and the vane portion and the interacting means.
The interaction means and the receiving means are not integral with the
Holding means for relative rotation between the receiving means and the interacting means
Rolling element closer to the blade between the inner and outer integral non-divided grooves to provide
A ball bearing assembly close to the blade including the inner and outer integral undivided grooves.
Body-to-body ball bearing assembly including inboard rolling elements remote from the blades between the body and body-to-blade to facilitate assembly of the retaining means.
And a centrifugal load in the operation of the propeller blades.
Preload means for applying preload to the holding means before applying
In connection with the outer groove of the ball bearing assembly and the thread of another threaded component
An element having mating threads, the outer side of the ball bearing assembly closer to the blade
Grooves and rolling elements close to the blades allow for separate threaded components from the element.
The relative rotational adjustment between the ball bearing assembly and the
Preload means having an element capable of generating a holding preload, and a separate threaded element
Locking means to prevent undesired relative rotational movement between the mounted components.
The relief area on the blade side is the groove inside the ball bearing assembly on the blade side
Of the ball bearing assembly formed in the receiving means, closer to the body, and closer to the blade.
Facilitating the loading of the rolling elements close to the blade between the inner and outer grooves, the relief area closer to the fuselage is provided with a relief area closer to the fuselage.
Formed by means of interaction towards the body, from the inside of the hub, a ball towards the body
Allows the loading of rolling elements near the fuselage between the inner and outer grooves of the bearing assembly.
Separate threaded components for ease of separation and separation from hub and achieve preload
Preload nut that is adapted to be tightened against the hub to
It is characterized by.

In one embodiment, the receiving means is not integral with the blade, and in another embodiment, the receiving means is integral with the blade.

In embodiments in which the receiving means is not integral with the blade, the assembly for holding and applying preload to the propeller blade holder is completely functionally separable from the propeller blade, and is a complex component. And reduce the complexity of assembly and maintenance, and reduce maintenance costs.

A receiving means that is not integral with the vane allows the mounting and retaining mechanism assembly and preload system to be adapted to multiple blade types without having to complicate the design of the blade root.

[0010] The individual receiving parts and the angular contact ball bearings between them and the propeller hub allow the use of a one-piece spherical groove and also the receiving, hub or blade of the propeller device. Threads can be eliminated.

By adapting the receiving means to provide the hydraulic actuator to provide a portion of the preload, a smaller, more manageable tool is available for tightening the preload nut at the preload of the receiver.

Thus, in accordance with a preferred embodiment of the present invention, functionally separable vanes and holding devices coexist and also allow for preloading of the holding mechanism, resulting in reduced cost and parts, and reduced maintenance complexity. A propeller device having a lowered propeller blade mounting retention system is provided.

[0013]Embodiment of the Invention  The propeller blade mounting and holding assembly of the present invention, designated by the numeral 10 in FIGS.
Is shown. Normally, the propeller blade holding assembly 10 is divided into four parts, a hub
It includes a part 12, a receiving part 14, a preload applying means 16, and a mounting and holding means 18. Receiving section
14 is located inside the hub arm 22. The receiving part 14 and the hub arm part 22
, Interact with the preload means 16 and the mounting and holding means 18. The holding means 18 is a receiving unit
14 and the hub arm 22.

Generally, the hub arm 22 has a cylindrical shape defined by an inner surface 24 and an outer surface 23 that extend radially about the axis of rotation of the vane and receiver.
As shown in FIG. 2, the hub arm 22 is usually cylindrical and has a hub barrel.
) 34. 2, the inner surface 24 of the hub arm 22 is
A hub arm shelf 30, including an outer first groove 32 near the fuselage, which is a single, non-segmented structure and has a ball groove relief region 33 near the fuselage; All of them extend circumferentially on the inner surface 24. A torso ball groove relief area 33 near the lower portion of the first groove 32 is circumferentially rounded or chamfered around the hub 12 to facilitate mounting of the torso ball bearing assembly 39. Used for Body end 6 on inner surface 24 of hub arm 22
In the vicinity of 1, a hub arm shelf 30 is formed which is substantially perpendicular to the second cylindrical side 31 and includes a first side 35 adjacent to the first groove 32. The hub arm shelf 30 extends circumferentially around the inner surface 24 of the hub arm portion 22 and is utilized to bottom the mounting and retaining assembly elements 36 to assist in preloading during assembly. used.

As shown in FIGS. 1 and 1A and 2, the mounting and retaining assembly element 36 is generally cylindrical in shape and has functionally shaped inner and outer surfaces, and as described below, The thread 37 on the surface and the outer second bearing groove 38 close to the blade, the stepped surface 41 for engaging the seal, and the rounded surface 43 have a central part, a top part and Include each on the bottom inner surface. As shown in FIGS. 1 and 1A, the upper end of element 36 is defined by a plurality of extensions 85 described below.

As shown in FIG. 2, the receiver 14 has an integral mounting joint 40 formed at the top end 42 of the receiver 14 for interacting with the propeller blades 44, thereby providing air The foil blade 44 can be removed from the propeller of the aircraft without affecting the preload of the blade mounting and retaining means 18. The mounting joint 40 includes a fastener opening 45 for engaging a fastener (not shown) for securing the propeller blades 44. A bulkhead 46 for supporting and strengthening the second joint 40 to which the propeller blades 44 are attached is provided on the bottom side 4 of the second attachment joint 40.
At 8 it is formed as an integral structure. A third groove 50 on the outer side, near the blade, is radially rounded or chamfered toward the blade-side end 53 of the receiving portion 14. The third groove 50 faces the second bearing groove 38 of the mounting and retaining assembly element 36 to form a ball groove 58 near the blade. The fourth groove 60 on the inner side near the body is provided with the receiving portion 14 near the end 61 on the body side.
At the above predetermined spacing, the fourth groove 60 is circumferentially rounded or chamfered around the outer side surface 52 of the receiving portion 14 where the first groove 60 of the hub arm portion 22 is formed.
The groove is formed on the opposite side to the groove, and is installed to form a spherical groove portion 59 near the body. In order to provide clearance for mounting and holding the receiving portion 14 inside the hub arm portion 22, a spherical groove portion 59 near the body and a spherical groove portion 58 near the blade are formed in the relief region 3.
Angular contact (angular contac) near the body, which is easy to install
t) used to secure the ball bearing assembly 39 and the angular contact ball bearing assembly 64 near the blade, which is easy to mount due to the relief area 63 near the ball groove 58 formed on the outside 52 of the receiving portion 14; Is done. The receiver 14 is preferably designed to accommodate the use of a hydraulic or mechanical actuator (not shown) used to change the pitch of the propeller blades 44 at the base.

Each of the body-side ball bearing assembly 39 and the blade-side ball bearing assembly 64, together with the body-side ball groove 59 and the blade-side ball groove 58, form an angular contact ball bearing device, and have a line of force. The angular positioning indicated by _CF permits the use of a single, undivided spherical groove. This eliminates the use of a split support ball groove in the prior art of U.S. Pat. No. 5,415,527. Each of the body-side ball bearing assembly 39 and the blade-side ball bearing assembly 64 allows rotation of the blade portion inside the hub arm portion 22. For a particular aircraft load, a rotating element and a ball groove shape are formed. The angle between the line of intersection of these lines of force indicated by the bearing ball grooves 58, 59 and the line C _F, filed different U.S. patents and many prior art bearings does not form an angle (non-angularly oriented bearings) Wider "wheelbase" or "cone of cont" similar to that disclosed in U.S. Pat. No. 5,118,256.
act) "is acceptable. Centrifugal loads, preloads, and bending loads, as well as thrust loads and torque loads, act according to conical contacts that provide a more stable blade mounting and retaining mechanism. Each of the ball bearing assemblies 39, 64, along with a hydraulic actuator (not shown), allows the pitch angle to be varied.

As shown in FIG. 2, the preload means 16 includes a ring-shaped preload nut 70 and a thread portion 7.
1 that engage and mate with the threads 37 of the mounting and retaining assembly element 36. The preload is achieved by pressing against the top surface 54 of the hub arm 22 and tightening the preload nut 70, thereby creating a load parallel to the axis of rotation of the propeller blades 44. Limiting the inward movement by loading the ball bearing assembly 64 outwardly through the element 36 against the bodyward ball bearing assembly 39;
Generates a force that applies a preload. The circumferential fixed seal 72 is attached to the hub arm 2.
2 between the top surface 54 and the load nut 70 to prevent leakage of lubricating oil contained in the hub arm for components of the propeller blade retaining mechanism and the blade pitch changing actuator. The maximum possible exposure of the lubricant on all interacting surfaces of the components of the mounting retainer enables the components of the propeller blade mounting retainer assembly 10 to maintain normal operation. It is.
A second circumferential stationary seal 74 supported and secured in place by a preload locking ring 76 is disposed between the preload nut 70 and the mounting and retaining assembly element 36.

The retaining ring portion 76 not only prevents the preload nut portion 70 from backing off the thread portion 37 of the mounting and retaining assembly element 36, but also provides a dynamic seal.
al) Supports 78, thereby preventing loss of preload of mounting and retaining means 18. As shown in FIGS. 1 and 2, the retaining ring 76 having its legs 77 extending between the preload nut 70 and the element 36 has a T-shaped cross-section and a circumferential Extending in the direction. Preferably, the retaining ring is split to facilitate mounting after the preload nut is in place. In the preferred embodiment, FIG.
As shown, ring 76 includes inner legs 79 defined by a plurality of fingers 81 separated by slots 83. The slot between the fingers 81 engages the extension 85 of FIG. 1A extending from the element 36. Bolts 86 are tightened through the top side 88 of the retaining ring 76 to secure the retaining ring 76 in place with respect to the preload nut 70. The engagement of the slot 83 with the extension 85 locks the retaining ring 76 in place with respect to the element 36. Thus, the double locking configuration of the locking ring 76 (i.e., the engagement of the bolt 86 with the preload nut 70 and the engagement of the slot 83 with the extension 85) is defined by the position of the preload nut 70 with respect to the thread 37. At the required preload position such as this, a fixed position between the preload nut and element 36 is obtained. The splittable nature and the multiple element / preload nut engagement positions of the retaining ring 76 allow for mounting at any relative position between the nut 70 and the element 36. As shown in FIG. 1, a spring-loaded dynamic seal 78 is disposed between the outer surface 87 of the receiving portion 14 and the stepped surface 41 of the mounting and retaining assembly element 36 to maintain the sealing contact pressure. A backup ring 82 made of a durable material, and the surface thereof is disposed between the fixed seal 74 and the preload nut 70, and functions as a support of the seal near the body. A second backup ring 84 is disposed between the kinetic seal 78 and the retaining ring 76 to reduce friction and prevent the kinetic seal 78 from being dragged on the retaining ring 76.

In the assembly shown, a dynamic seal 78 and a backup ring 84 are mounted toward the blade-side end 53 of the outer side 87 of the receiver 14. The mounting and retaining element 36 with the preload nut 70, the stationary seals 72, 74 and the backup ring 82 provide a groove 60 near the fuselage and a groove near the blade so that the ball bearing assembly 64 near the blade can be pressed into the bearing groove 38. It slides on the receiving part 14 in the middle of the groove 50. The ball bearing assembly 64 close to the blade is inserted into a predetermined position using the relief area 63. Blade receiver 14 and bearing assembly 64 slide into hub arm 22 adjacent inner surface 24. Element 36
Bottom is on the side surface 35 of the shelf 30. A torso bearing assembly 39 is mounted from inside the hub utilizing the relief area 33. As described above, the assembly is pushed outward against the hub arm 22. The preload nut 70 is manually tightened at the threaded portion 37 of the element 36 to secure the component in place until the next application of preload and to tighten the component against the surface 24 of the hub arm 22. . The preload can be performed using only the preload nut 70 or, alternatively, incorporating a thickened septum 46 in the receiving portion design to reduce the hydraulic actuator application to the surface 48 of the septum 46 or the receiving portion 14. It is adapted as an assembly tool that opposes the base 90 and provides some significant retention preload. This option allows the preload nut 70 to be tightened to the hub arm 22 using a smaller tool. Thus, the required preload is provided by a hydraulic actuator, if desired, and by a preload tool (not shown) using the septum 46 or the base 90 of the receiver 14. The preload nut 70 is tightened as necessary, and the application of the preload is completed. If using a hydraulic actuator (not shown), remove it. Depending on the deflection of the hub, it may be necessary to apply a preload in stages. Then, not only the motion seal 78 and the fixed seals 72 and 74, and the fixed ring 76 and the bolt 86 but also the respective backup rings 84 and 82 are attached to complete the assembly.

In operation, each of the inner and outer ball bearing assemblies 39, 64 allows the blades to rotate within the hub arm 22, and controls the pitch and the number of revolutions per minute of the propeller. When the pitch is changed by a hydraulic actuator (not shown) different from the actuator for applying the preload, the ball bearing assembly 39,
64 is rotatable in the circumferential direction around the hub arm 22.

In another embodiment 110 according to the present invention shown in FIG. 3, the receiving portion 114 is formed as a unitary structure as the root 191 of the propeller blade 144, and is not described again here, but is similar in the drawing. They include all other features according to the invention described above. Additional features shown in FIGS. 1 and 2 but not shown in FIG. 3 are also part of embodiment 110, but are not described here. As is known in the art,
During the blade formation process, the blade is formed as an integral structure with the receiver 114. As described above, the integral non-divided groove 13 differs from the prior art.
The use of 2, 138, 150 and 160 prevents deterioration of the groove. Also,
An angular contact ball bearing assembly is used.

A first advantage of the present invention is that each part of the assembly is fully functionally separable from the propeller blades, reducing the complexity of parts and tools. Reducing complexity results in lower costs. Another advantage of the present invention is that the propeller blade preload and mounting and retaining system allows the mounting and retaining mechanism assembly and preload system to be adapted to multiple blade types without the need to complicate blade root design. It is to include. A further advantage of the present invention is the use of angled and contacting ball bearings and individual receivers between the mounting and retaining assembly and the preload system and propeller hub, thereby allowing the use of integral grooves and split grooves. Avoids the potential problems associated with the joints, which include threads on the hub, blades, or the receiver of the propeller assembly. A further advantage of the present invention is to use a receiver with a hydraulic actuator adapted to provide a portion of the preload so that a smaller, more manageable tool can be used to tighten the preload nut with respect to the receiver preload. It was done.

Although the present invention has been described with respect to particular embodiments thereof, it is to be understood that various changes and modifications can be made to this embodiment without departing from the scope of the appended claims. The trader will understand.

[Brief description of the drawings]

FIG. 1 shows a hub arm portion, a receiving portion, an attachment holding mechanism, and a preload applying mechanism (preload mechanis).
FIG. 4 is a three-dimensional cutaway view of the propeller blade mounting and holding assembly including m).

FIG. 1A is an enlarged perspective view of an element indicated by an arrow 1A in FIG. 1;

2 is a cross-sectional view of the propeller blade retaining assembly of FIG. 1;

FIG. 3 is a cross-sectional view of a propeller blade retaining assembly in another embodiment.

[Procedure amendment 2]

[Document name to be amended] Drawing

[Correction target item name] Fig. 1

[Correction method] Change

[Correction contents]

FIG.

[Procedure amendment 3]

[Document name to be amended] Drawing

[Correction target item name] FIG. 1A

[Correction method] Change

[Correction contents]

FIG. 1A

──────────────────────────────────────────────────続 き Continuing the front page (72) Inventor Saul, Matthew Sea, Connecticut, U.S.A. 06096-1010 Granby Eric Drive 12 (72) Inventor Korey, Thomas G. 06078, Connecticut, U.S.A.

Claims (34)

[Claims] 1. A propeller blade mounting and holding assembly for use with a propeller having a hub that rotates about a propeller axis, comprising: receiving means for mounting the blade to the hub; and Means for interfacing with said hub portion, wherein said receiving means is located within said interaction means and is not integral with said vane portion and said interaction means; The receiving means relative to means for interacting so as to permit relative rotational movement and means for applying a preload to the mounting and holding means prior to applying a centrifugal load in the operation of the propeller blades. Means for mounting and holding, wherein the blades are separable from the receiving means without impairing the operability of the mounting and holding means, A propeller blade mounting and retaining assembly. 2. The hub portion includes a hub body, the interaction means includes a hub arm connected to the hub body, and the hub arm and the receiving means interact using the mounting and holding means. The propeller blade mounting and retaining assembly according to claim 1, wherein: 3. The propeller blade mounting and retaining assembly according to claim 2, wherein said hub arm portion further comprises a hub arm cavity with means for supporting said mounting and retaining means. 4. The propeller blade mounting and retaining assembly according to claim 1, wherein said receiving means includes a mounting joint for enabling said mounting and dismounting of said blade portion to said receiving means. 5. The propeller blade mounting and holding assembly according to claim 4, wherein said receiving means further includes a blade receiving portion partition wall for supporting said blade receiving portion. 6. The propeller blade mounting and retaining assembly according to claim 4, wherein said receiving means further comprises a receiving base with means for engaging an actuator for changing the blade pitch. 7. The propeller according to claim 1, wherein said receiving means and said interacting means define a body-side and blade-side relief area for facilitating assembly of said mounting and holding means. Blade mounting and holding assembly. 8. A blade-to-blade ball bearing assembly, wherein said mounting and holding means includes a blade-to-blade rolling element to permit relative rotational movement between said receiving means and said interaction means. 8. The propeller blade mounting and retaining assembly according to claim 7, including a body fuselage ball bearing assembly including rolling elements. 9. The mounting and retaining means further comprises an element having a blade-side groove and a thread defining a part of the blade-side ball bearing assembly;
By engaging the means for applying a preload to the threads, the blade-side grooves and the blade-side rolling elements are loaded against the body-side ball bearing assembly. The propeller blade mounting and retaining assembly of claim 8, wherein said element allows for the generation of a mounting retainer preload. 10. The method according to claim 1, wherein the mounting and holding means is provided between the receiving means and the element;
An angular contact ball bearing ball groove portion closer to the body and closer to the blade formed between the receiving means and the interaction means, wherein each of the ball grooves closer to the body and to the blade has an integral non-divided groove. 10. The method according to claim 9, wherein
4. The mounting and holding assembly for a propeller blade according to claim 1. 11. The body-side and blade-side rolling elements include angular contact ball bearings that engage the body-side and blade-side ball grooves to rotate vanes in the hub arm. The propeller blade mounting and retaining assembly according to claim 10, wherein: 12. The means for applying a preload includes a thread and a preload nut extending from the mounting and holding means to the outside of the interaction means, wherein the preload nut is near and above the hub arm. 3. The propeller blade mounting according to claim 2, wherein the preload is established by tightening the preload nut on the threaded portion against the hub arm portion and pulling the mounting holding means. Holding assembly. 13. The means for applying a preload includes a preload nut,
10. The propeller blade mounting and holding assembly according to claim 9, further comprising fixing means for fixing a required rotational position between the preload nut and the thread portion. 14. The means for applying a preload includes a preload nut engaged with the thread, and wherein the mounting and retaining means is for immersing substantially all of the connecting surfaces in a lubricating oil as much as possible. The assembly of claim 9, further comprising at least two stationary seals disposed between the element and the preload nut and between the preload nut and the interaction means. 15. The mounting and retaining assembly for a propeller blade according to claim 14, wherein said mounting and retaining means further comprises a dynamic seal disposed between said receiving means and said element. 16. The propeller blade mounting and retaining assembly according to claim 15, wherein said mounting and retaining means further comprises means for avoiding damage to said dynamic seal. 17. The apparatus of claim 13, wherein the means for applying a preload further comprises a mounting and holding device for fixing the fixing means in place with respect to the preload nut and thread. Propeller blade mounting and retaining assembly. 18. The receiving means includes a main body having an inner end located within the hub portion and an outer end located outside the hub portion, wherein the outer end portion comprises: Means for engaging the blade portion without the blade portion entering the hub portion, and means for applying the preload, wherein the means for applying the preload includes the mounting and holding member. Providing a preload on the means and being located inside the means for engaging between the inner and outer ends so that the preload is not disturbed during the mounting and dismounting of the wings. The propeller blade mounting and retaining assembly according to claim 1, wherein: 19. The means for applying a preload includes an element and a preload nut engaged between the main body and the interaction means, wherein the element extends outside the interaction means. 19. The propeller blade mounting retainer of claim 18, wherein the preload nut is engagable with the thread to apply a preload to the mounting retainer means. assembly. 20. A propeller blade mounting and holding assembly for use with a propeller having a hub that rotates about a propeller axis, comprising: receiving means for mounting the blade to the hub; and Means for interacting with said hub portion, wherein said receiving means is located within said interacting means and is integral with said blade and not integral with said interacting means. Means for interacting so as to allow relative rotational movement, and means for applying a preload to said mounting and holding means prior to applying a centrifugal load in the operation of the propeller blades. Means for mounting and holding the receiving means, wherein the mounting and holding means is capable of relatively rotating between the mounting and holding means and the interaction means. An angular contact ball bearing assembly for facilitating mutual rotational movement between said receiving means and said interacting means, said angular contact ball bearing assembly including an integral, non-divided groove. Propeller blade mounting and holding assembly. 21. The hub includes a hub body, the interaction means includes a hub arm connected to the hub body, and the hub arm and the receiving means are connected using the mounting and holding means. 21. The propeller blade mounting and retaining assembly of claim 20, wherein: 22. The propeller blade mounting and retaining assembly according to claim 21, wherein said hub arm portion further comprises a hub arm cavity with means for supporting said mounting and retaining means. 23. The receiving means according to claim 22, wherein said receiving means is mounted in said hub arm cavity and includes a septum for strengthening said receiving means.
A mounting and retaining assembly for a propeller blade according to claim 1. 24. The receiving means further comprising a receiving base with means for engaging an actuator for changing blade pitch.
4. The mounting and retaining assembly for a propeller blade according to claim 3. 25. The propeller according to claim 20, wherein said receiving means and said interacting means define a body-side and blade-side relief area to facilitate assembly of said mounting and holding means. Blade mounting and holding assembly. 26. A blade-side ball bearing assembly, wherein the angular contact ball bearing assembly includes a blade-side rolling element that enables relative rotational movement between the receiving means and the interaction means, and a fuselage. 26. The propeller blade mounting and retaining assembly of claim 25, comprising a body fuselage ball bearing assembly including a rolling element. 27. The mounting and retaining means further includes an element having an integral non-partitioned groove and thread near the blade defining a portion of the ball bearing assembly near the blade, wherein the thread is preloaded. By engaging the means for adding a fin, the blade-side groove and the blade-side rolling element are mounted and held when the element is loaded against the body-side ball bearing assembly. 27. The propeller blade mounting and retaining assembly according to claim 26, wherein a preload is generated. 28. The method according to claim 28, wherein the mounting and holding means comprises:
28. The propeller blade mounting and holding assembly according to claim 27, further comprising an integral angular contact non-divided spherical groove near the fuselage and blade formed between the receiving means and the interaction means. . 29. The means for applying a preload includes a thread and a preload nut extending from the mounting and holding means outside the interaction means, wherein the preload nut is near and above the hub arm. 22. The mounting of a propeller blade according to claim 21, wherein said preload is established by tightening said preload nut on said threaded portion against said hub arm portion and pulling said mounting and holding means. Holding assembly. 30. The means for applying a preload comprises a preload nut, a thread portion, and a fixing means for fixing a required rotational position between the preload nut and the thread portion. 28. The propeller blade mounting and retaining assembly of claim 27, comprising: 31. The means for applying a preload includes a preload nut engaging the thread, and the mounting and retaining means for immersing substantially all of the interaction surfaces in a lubricating oil as much as possible. 29. The propeller blade mounting and retaining assembly according to claim 28, further comprising at least two static seals disposed between said element and said preload nut and between said preload nut and interaction means. . 32. The apparatus of claim 31, wherein the means for applying a preload further comprises mounting and retaining bolts for fixing the fixing means in place with respect to the preload nut and thread. Propeller blade mounting and retaining assembly. 33. The means for applying a preload includes a thread and a preload nut extending from the mounting and holding means to a location outside the interaction means, wherein a preload opposes the hub arm. 22. The propeller blade mounting and retaining assembly according to claim 21, wherein the assembly is achieved by engaging a nut and a thread. 34. The propeller blade mounting and retaining assembly according to claim 31, wherein said mounting and retaining means further comprises a dynamic seal disposed between said receiving means and said element.